Multiple-tube pressurized tank for missile



April 30, 1957 F. G. DENISC'JN, JR

MULTIPLE-TUBE PRESSURIZED TANK FOR MISSILE 2 Sheets-Sheet 1 IF: -1-

Filed June 1, 1954 INVENTOR. Frank E- 1] an is 011-111.

ATTORNEYS MULTIPLE-TUBE PRESSUR IZED TANK FOR MISSILE n 2 Sheets-Sheet 2Filed June 1, 1954 Fit -4- M m. G E 7 W s N Z Z N m w m 3 I. w 2 w l l 7w. M. .flfl 3 //5 w? x L L M e 3 w! 5 2 2 INVENTOR. I Frank E.1121115011 11- AT TOENEYS 2,790,489 MULTIPLE-TUBE PRESSURIZED TANK FORMISSILE Frank G. Denison, Jr., Pasadena, Calif assignor to the UnitedStates of America as represented by the Secretary of the ArmyApplication June 1, 1954, Serial No. 433,853 12 Claims. (Cl. 158-501)This invention is a multiple-tube fuel storage tank for self-propelledmissiles.

An object of the invention is to provide a multipletube storage tank forstoring liquids or gas under pressure.

Another object of the invention is to provide an assembly for bearingmajor internal structural loads when assembled with the motor andwarhead of a self-propelled missile.

Another object of the invention is to provide an assembly in which theairframe and tubes are assembled to absorb stresses imparted thereto inflight of the missile.

Other objects and advantages will be apparent from the followingdetailed description and the accompanying drawings, in which:

Figure l is a longitudinal sectional view of the multiple-tube tanktaken on the line 11 of Figure 2 and showing parts in elevation,

Figure 2 is an end view of the tank as viewed from the left-hand side ofFigure 1,

Figure 3 is an end view of the tank as viewed from the right-hand sideof Figure 1,

Figure 4 is an enlarged sectional view of parts of the tank taken on theline 44 of Figure 5,

Figure 5 is sectional view of the parts shown in Figure 4 taken on theline 5-5 of Figure 4, and

Figure 6 is a diagrammatic view showing the direction of transferral ofloads from the mounting rings of the tubes and from one tube to another,during flight, in'a self-propelled spin type missile into'which the fueltank is assembled.

In the drawings, wherein for the purpose of illustration, is shown oneform of the invention, the reference character 10 indicates an airframehaving a longitudinal axis AA. The airframe comprises a cylindricalsheet metal casing 11 reinforced at its ends by rings 12 and 13. For'thesake of clarity the end of airframe 10 carrying ring 12 will be calledthe forward end of the airframe and the end carrying ring 13 will becalled the rearward end. Overlying sectional brackets 14 secure therings 12 and 13 to the casing 11 by rivets or. other suitable means.

An outer layer of tubes 15 are held in parallel relationship each withthe other and with the longitudinal axis of the casing 11. The tubes 15are securely held at their forward ends in hangers 16 and at theirrearward ends in hangers 17. Each hanger has an arcuate seat 18 forreceiving the forward and rearward ends, respectively, of tubes or tanks15. Each tank is sealed at its forward end by a head 19. The heads 19are formed with forwardly extending flanges 20 which are also receivedin the seats 18 of forward hangers 16 and secured therein by bolts 21.In the present application of the invention the tanks 15 will receivegas under pressure and therefore thebulkheads 19 are provided with screwthreaded openings 22 formed in bosses 23 to which a screw threaded pipecoupling '24 is attached. A manifold 25, see Fig- United Sates Patent 02,790,489 Patented Apr. 30, 1957 "ice,

conducts gas pressure'to the tanks 15 from a source (not shown).Radially extending from the manifold 25 are branches 26 which serve touniformly distribute to the tubes 15 gas pressure and uniformly deliverthe gas pressure to a liquid fuel reservoir, to be later described;during flight of a self-propelled missile in which the tank isinstalled. When-used solely as a storage tank additional valves (notshown) are installed in the branches 26 so that individual'tanks maybedepleted as desired. The rearward ends' of tanks 15 are sealed bybulkheads" 27 which-also have flanges 28 held in the arcuate seats ofrear hangers 17 together with the rear ends of tanks 15 and secured bybolts 29 extending through the hang ers 17.

An inner bank of tubes 30, in parallel relationship and" close contactwith tubes 15, completely fills the area inside the outer tubes 15 and'each tube 30 is sealed at its forward end by a bulkhead 31. Eachbulkhead 31 is formed with a central boss 32 having a screw threadedopening 33 for screw threadedly receiving a pipe coupling 34. Formedwith bulkheads 31 and extending forwardly therefrom are flanges 35. Boltholes 36, near the forward ends of tubes 15 and 30 extend therethroughand through the flanges 20 and 35 at points of surface contact ortangency of adjacent tubes. Bolts 37 pass through the holes 36 andsecurely bind the forward ends of thetubes together. At their rearwardends each tube 30 isclosed by a bulkhead 39 formed with a central boss40 in which a screw threaded opening 41 is formed. Formed with the heads39 and extending rearwardly therefrom are flanges 39a. Bolt holes 54,near the rearward ends of tubes 30 extend therethrough and through theflanges 28 and 39a at points similar to the bolt holes 36 in theforward. end of the tubes. Bolts 53 pass through the holes 54 and'securely bind the rearward ends of the tubes together. In fluidcommunication with the pipe fitting 34 and the manifold 25 are shortpipe couplings 38 for admitting pressure to the inner bank of tubes 30for a purpose to be later pointed out. A screw threaded pipe coupling 42is secured in the'boss 40 and to a branch of a manifold 43. Themanifolds 25 and 43 may be of any configuration as best suited to theparticular use to which the tank is put, whether for gas storage or as afuel supply reservoir for a rocket missile. In the present illustrationeach tube 30 of the central bank of tubes has slidably receivedtherein'a piston 44 which will divide its interior into two discretecompartments 45 and 46 of reciprocably variable volume. In use thecompartments 46 are filled with a liquid fuel through the openings 41 inbosses 40 and the pistons are thereby moved to the forward ends of tanks30, thereafter the manifold 43 is attached. Gas pressure is applied tothe tanks 15 and subsequently to the compartments 45 as the liquid fuelin compartments 46 is consumed in a motor (not shown). When the fuel incompartments 45 is exhausted and gas pressure from tubes forces pistons44 rearwardly a tapered plug 47 formed centrally of each piston 44 willclose the outlet opening 48 formed in the coupling 42 to seal thecompartment 46.

Reinforcing plates 49 are rivetted to the forward ring 12 and carrytruss rods 50 for securing the forward end of airframe 10 to a warhead(notshown) and a similar structure comprising reinforcing plates 51 andtruss rods 52 secure the air frame to a rocket motor (not shown).

Figure 6 is an exploded fragmentary view of parts of the assembly toillustrate the direction of stresses to which the assembly is subjectedas will now be discussed.

In flight, torsional stress generated outside the multicell tank istransferred through the mounting rings 12 and 13 and the bolts Hand 29to the individualvtubes. The tubes absorb this stress by undergoingtorsional and difiersorbed by the tubes according to their individualdisplacement from the neutral axis of the airframe through developmentwithin individual tubes of simple compression or tension, differentialbending. and associated vertical shear.

In assembly and operation the pistons 44. are moved to the forward endsof'tanks 30 and the compartments are filledwit'h liquid fuel. Themanifold 43 then is connected to the heads 39 by means of the pipecouplings 42, after which the free end of the manifold is connected to arocket motor. The tubes 15 can be pressurized at any desired time beforeflight of the missile and the free end of the manifold 25 sealed. Gaspressure in the tubes 15 is then applied to the compartment 45 by way ofthe manifold 25' and the short couplings 38 through the bulkheads'31'into the forward ends of tubes 30. Any well known means for releasingthe liquid fuel to the rocket motor may be employed.

It is to be understood that the form of the invention, herewith shownand described, is to be taken as a preferred example of the same, andthat various changes in the shapfi, Size and arrangement of parts may beresorted to without departing from the spirit of the invention, or thescope of the subjoined claims.

Having now fully disclosed the invention, what I claim and desire tosecure by Letters Patent is:

I. In a pressure tank assembly for a self-propelled vehicle, a pair ofcylindrical tanks each having an outwardly-flanged head integrallysecured within an end to define circular rims, a pair of duplicatehangers each having an arcuate slot to embrace the rim of a respectivetank,

said hangers having generally flattened contacting surfaces, and boltspassing through aligned holes in said rims and hangers to rigidly securesaid tanks in contigous' spaced parallel relation with said surfaces incontact.

2. In a pressure tank assembly, first and second cylindrical tanks eachhaving a pair of flanged heads secured within the respective ends toform circular rims, first and second pairs of duplicate hangers eachhanger having an arcuate slot receiving and embracing the rim of arespective tank, each hanger having generally parallel flat external andinternal faces in planes parallel with the axis of its tanks, and a pairof bolts extending through the flat surfaces of a respective pair ofhangers and the rims of the tanks embraced thereby, said bolts acting toclamp the external faces of each pair in contacting relation and torigidly secure said tanks in spaced parallel relation.

3. In a pressure tank assembly for a self-propelled missile, a pair ofcylindrical tanks having inwardly flanged heads secured within therespective ends thereof to form circular rims, first and second pairs ofhangers each having an arcuate slot to receive and embrace the rim of arespective tank, and external and internal flats in respective radiallyspaced planes parallel with the axis of its tank, and bolts passingthrough aligned holes in the flats of each pair of hangers and the rimsembraced thereby, whereby to rigidly unite said tanks in spaced,parallel, side. by side relation.

4.v An assembly as recited in claim 3,.said hangers each having agenerally flat attaching flange at its end exteriorly of the tanks andlying in a plane normal to the axis of the tanks, a pair of fiatsupporting rings, and means rigidly attaching each flange insurfaceto-surface contact with a corresponding one of said rings.

5. In a pressure tank assembly for a self-propelled missile, a firstplurality of cylindrical tanks each-having an outwardly flanged headsecured within a respective end to form therewith a circular rim, apluralityof pairs of hangers each arcuately slotted to receive the rimof a respective tank and having a generally flat exterior surface, boltspassing through aligned holes in the rims and surfaces of the'respectivepairs of hangersandrims to rigidly unite the tanks with the surfaces ofeach pair of hangers in contact whereby saidtanks are unite'd inparallel relationcircumferentially about acommon central axis, eachcontact with a pair of tanks of said first plurality, and

bolt means passing through the rims of each of said tanks of said secondpluralityand the corresponding tanks of said first plurality at thepoints of tangency. l

7. An assembly of storage tanks for self-propelled missiles comprising aframe having a longitudinal rotational axis, a first circumferentiallydisposed group of tanks within said frame each said tank being sealed atits forward and rearward ends, means securing said tanks to said frameand to each other in parallel relationship to each other and to thelongitudinal axis of said frame to resist relative displacement due totorsional and axial stresses in the assembly during flight of themissile, a second group of tanks positioned centrally of said frame andsaid first group of tanks in parallel relationship with each; other andwith said first group of tanks each said tank being sealed at itsforward and rearward ends, means securing all of said tanks to eachother and to said first group of tanks at contiguous points todistribute and absorb said stresses, inlet manifold means. connected to'the forward ends of all of said tanks for admitting fluid underpressure, and outlet manifold means connected to the rearward ends ofsaid second group of tanks.

8. An assembly of storage tanks for self-propelled missiles comprising aframe, a first group of tanks within said frame, first and secondreinforcing means secured to said frame at opposite ends thereof, pinand bracket means carried by said first and second reinforcing means tosecure said group of tanks thereto and to each other to resist relativedisplacement due to torsional and axial stresses during flight of themissile, a second .group' of tanks positioned adjacent and in parallelrelationship to said first group of tanks, and pin means connecting saidfirst and second groups of tanks at contiguous points on their outersurfaces to distribute and absorb said stresses.

9. An assembly of storage tanks for self-propelled missiles comprising aframe including a first reinforcing means secured to one end of saidframe, a second reinforcing means secured to the opposite end of saidframe, a first plurality of tanks supported at their opposite ends tosaid first and second reinforcing means and to each other, a secondplurality of tanks secured to said first plurality of tanks and to eachother to provide a single rigid assembly, inlet manifold means connectedto the inlet ends of all of said tanks for admitting fluid underpressure, and outlet manifold means connected to the outlet ends of saidsecond plurality of tanks.

10. An assembly of storage tanks for self-propelled missiles comprisinga hollow cylindrical frame including a first reinforcing ring secured toone end of said frame, a second reinforcing ring secured to the oppositeend of said frame, a first group of tanks circumferentially disposedwithin said cylindrical frame in surface contact with the innercircumference thereof and having their longitudinal axes parallel withthe rotational axis of said cylindrical frame toform a centrallongitudinally extending cavity, bracket means having an arcuate seatsecured to both said reinforcing rings for receiving the respective endsof each said tank, a second group of tanks in said central longitudinalcavity having their longitudinal axes parallel with the longitudinalaxes of said first group of tanks, separate pin means for securingadjac'ent tanks together at contiguous points, means for supplyingpressurized fluid into the tanks, at one end thereof, and outlet meansconnected to the opposite ends of said second group of tanks.

11. An assembly of storage tanks for self-propelled missiles comprisinga frame, a first group of tanks within said frame to receive fluidpressure, first and second re inforcing means secured to said frame atopposite ends thereof, pin and bracket means carried by said first andsecond reinforcing means to secure said first group of tanks thereto andto each other, a second group of tanks to receive liquid fuel positionedwithin and in parallel relationship to said first group of tanks, apiston slidable in each said tank to separate the fluid pressure fromthe liquid fuel and provide a separate chamber for said liquid fuel, pinmeans connecting said first and second groups of tanks at contiguouspoints on their outer surfaces, an inlet manifold structure connected toall of the tanks at one end of the assembly whereby all of said tanksare pressurized, and an outlet manifold structure connected to saidsecond group of tanks at the opposite end of the assembly whereby theliquid fuel contained therein is led to a point of usage when fluidpressure from said first groups of tanks is applied to said pistons.

12. An assembly of storage tanks for self-propelled missiles comprisinga frame, a first group of tanks within said frame to receive fluidpressure, first and second reinforcing means secured to said frame atopposite ends thereof, pin and bracket means carried by said first an'dsecond reinforcing means to secure said first group of tanks thereto andto each other, a second group of tanks to receive liquid fuel positionedwithin and in parallel relationship to said first group of tanks eachtank at its outlet end carrying a bulkhead having an outlet opening, avalve seat positioned in said opening, a piston slidable in each saidsecond group of tanks to separate said fluid pressure from said liquidfuel, a tapered valve member carried by said piston engageable with saidvalve seat to seal the outlet opening when said tank is empty, pin meansconnecting said first and second groups of tanks at contiguous points ontheir circumferences, an inlet manifold structure connected to all tanksat the pressure inlet ends thereof whereby all of said tanks arepressurized, and an outlet manifold structure connected to said secondgroup of tanks at the outlet ends thereof to conduct said liquid fuel toa point of usage when fluid pressure from said first group of tanks isdirected to said pistons.

References Cited in the file of this patent UNITED STATES PATENTS1,283,482 Durkee Nov. 5, 1918 FOREIGN PATENTS 32,216 Denmark Aug. 24,192.3

